不同攻角和翼型的简化角冰特征参数的气动数值模拟

Aerodynamic Numerical Simulation of Characteristic Parameters of Simplified Horn Ice at Different Angles of Attack and Airfoils

选取常规翼型NACA23012、自然层流翼型NACA64-215和超临界翼型RAE2822,以冰角高度、冰角宽度,冰角端部形状以及冰角之间的连接情况4个参数来研究角冰对不同翼型在不同攻角下的升阻力系数的影响。结果表明,角冰的下冰角是影响翼型升阻力系数的主要原因之一,且不同翼型对参数的敏感性不同。同时,增加预测模型的升力性能可以通过选择半圆形的冰角端部形状、增加冰角之间的连接和减小冰角高度来实现。

This paper selects the conventional airfoil NACA23012,natural laminar flow airfoil NACA64-215 and supercritical airfoil RAE2822,with four parameters including the height,width,end shape of horn-ice,and connection between horns,to study the influence of these four parameters on the lift/drag coefficient of different airfoils at different angles of attack.The results show that the lower horn of horn-ice is one of the main factors affecting the coefficient,and the sensitivity of different airfoils to parameters is different.The lifting performance of the prediction model can be increased by selecting the semicircle end,adding the connection between horns and decreasing the height of the horn-ice.